Gas turbine engine, fuel nozzle assembly and method

Abstract

A gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement wherein the combustion section includes: a combustor liner at least partially defining a combustion chamber; a wall coupled to the combustor liner; a first fuel supply unit that supplies a first fuel; a gas fuel supply part for supplying gaseous hydrogen fuel; and a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply and the gaseous hydrogen fuel supply, the fuel nozzle assembly comprising: a main mixer; and a fuel nozzle, the fuel nozzle comprising: an outer wall defining a guide channel and an outer wall fuel orifice discharging at least one of the first fuel or the gaseous fuel radially outward into the main mixer; and the secondary mixer is arranged in the guide channel.

Description

Technical Field

[0001] This topic generally relates to gas turbine engines with fuel nozzle assemblies. Background Technology

[0002] A turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades, which in turn rotates a compressor, thus supplying compressed air to the combustor for combustion. The combustor can be located within the turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0003] Historically, hydrocarbon fuels have been used in the combustors of turbine engines. Typically, air and fuel are fed into the combustion chamber, mixed, and then the fuel is burned in the presence of air to produce hot gases. These hot gases are then fed into the turbine, where they are cooled and expanded to generate power. Byproducts of fuel combustion often include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x Carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including sulfur oxides (e.g., SO2 and SO3).

[0004] To reduce unwanted environmental byproducts, other fuels, such as hydrogen, are being explored. Hydrogen, or hydrogen mixed with another element, has a higher flame temperature than conventional hydrocarbon fuels. In other words, hydrogen or hydrogen-blended fuels typically have a wider combustible range and a faster combustion rate than conventional hydrocarbon-based fuels. Attached Figure Description

[0005] In the attached diagram:

[0006] Figure 1 This is a schematic diagram of a gas turbine engine having a compression section, a combustion section, and a turbine section, based on the various aspects described herein.

[0007] Figure 2 It is based on the various aspects described in this article along line II-II. Figure 1 A schematic diagram of the combustion zone.

[0008] Figure 3 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly connected to the combustion chamber according to the various aspects described herein.

[0009] Figure 4 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0010] Figure 5 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0011] Figure 6 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0012] Figure 7 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0013] Figure 8 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0014] Figure 9 This is a schematic cross-sectional view showing a portion of the fuel nozzle assembly according to the various aspects described herein.

[0015] Figure 10 This is a flowchart illustrating a method of operating a gas turbine engine according to the various aspects described herein. Detailed Implementation

[0016] The aspects disclosed herein relate to burners. In some aspects, the disclosed burners and fuel nozzle assemblies can be used with gaseous fuels, such as hydrogen. Gaseous fuels, including hydrogen, diffuse / disperse at a faster rate than atomized liquid fuels. This can result in less mixing time for the gaseous fuel, shorter fuel mixing tube lengths, and a flame from the gaseous fuel is more likely to spread further and faster. This increases the risk of flashback and flame persistence (e.g., in the nozzle or mixer) and enhances flame control and flame propagation limitation by controlling the dispersion of the gaseous fuel.

[0017] In addition to those shown in the accompanying drawings, this disclosure contemplates many other possible aspects and configurations. The disclosed fuel nozzle can be effectively used with a variety of fuels, such as liquid fuels (e.g., Jet-A) and gaseous fuels (e.g., hydrogen). Fuel can be discharged by the fuel nozzle at the same time or at different times. Compared to other designs, the disclosed fuel nozzle can provide better flame stability, lower flame temperature, reduced flashback, reduced flame sustaining, and lower NOx emissions. x Emissions. Distributed fuel injection from disclosed fuel nozzles (such as radial distributed fuel injection, axial distributed fuel injection, or both) can promote combustion stability and reduce NO. x Emissions and improved durability. Limiting flashback and flame hold can allow the use of more reactive fuels (such as hydrogen), promote the use of more reactive fuels by limiting wear on engine components, or both. Increasing mix time can provide a more uniform temperature distribution and lower peak temperatures, which can limit NO. x emission.

[0018] During certain phases of flight (such as approach), using hydrogen fuel alone can limit coking by removing unburned liquid fuel from the combustion zone. During certain phases of flight (such as cruise and approach), using hydrogen fuel alone can achieve zero carbon emissions (e.g., zero CO2). Using hydrogen fuel can shorten burner length by reducing mixing time, as hydrogen fuel mixes with air much faster than conventional fuels (such as Jet-A). Using hydrogen fuel alone at low power levels can limit or prevent smog. During at least some phases of flight (such as takeoff and climb), using conventional fuels (such as liquid Jet-A fuel) can limit temperature, improving durability and limiting NO. x emission.

[0019] For illustrative purposes, this disclosure will be described in relation to turbine engines. However, it will be understood that the aspects of the disclosure described herein are not limited thereto. The combustors described herein can be implemented in a variety of engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0020] For the burner and fuel nozzle assemblies described herein, gaseous hydrogen fuel can be used without the need for a diluent. In some embodiments, no diluent is added to the combustion chamber, and the fuel is substantially entirely diatomic hydrogen without diluent. As used herein, the term "substantially entirely" to describe the amount of a particular element or molecule (e.g., diatomic hydrogen) means at least 99% (by mass) of the described portion of the element or molecule, such as at least 97.5%, at least 95%, at least 92.5%, at least 90%, at least 85%, or at least 75% (by mass) of the described portion of the element or molecule. In some examples, the fuel is entirely (e.g., 100%) hydrogen (by mass).

[0021] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0022] Terms such as "first" and "second" can be used interchangeably to distinguish one component from another, and are not intended to indicate the location or importance of individual components.

[0023] The terms "front" and "rear" refer to relative positions within a gas turbine engine or carrier, and specifically to the normal operating posture of the gas turbine engine or carrier. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine exhaust outlet.

[0024] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward / front can indicate upstream, and backward / rear can indicate downstream.

[0025] The term "fluid" can refer to either a gas or a liquid. The term "fluid connection" means that fluids can establish a connection between specified areas.

[0026] In the context of gas turbine engines, the term "nozzle" is used in various ways. In this application, "nozzle" refers to a component having a portion fluidly connected to a fuel supply section and having at least one portion fluidly connected to a burner section, burner bushing, combustion chamber, or a combination thereof.

[0027] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0028] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connecting references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connecting reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0029] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0030] The use of “and” and “or” will be interpreted broadly. For example, but not limited to, the use of “and” does not necessarily require all the elements or features listed, and the use of “or” is inclusive unless the structure is illogical.

[0031] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” “substantially,” and “basically” are not limited to the specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture parts and systems. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0032] As used herein, “proximity” is a descriptor used to locate the parts described herein. Furthermore, the term “proximity” means that the part is closer to or closer to the referenced part than the following part. For example, “first orifice is close to the wall” or “first orifice is upstream of second orifice” means that the first orifice is closer to the wall than the second orifice.

[0033] Additionally, as used herein, "controller" can include components configured or adapted to provide instructions, control, operation, or any form of communication to an operable component to achieve its operation. A controller can include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), proportional-resonant controllers (PR), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), and combinations thereof. Non-limiting examples of controllers can be configured or adapted to run, operate, or otherwise execute program code to affect operational or functional outcomes, including performing various methods, functions, processing tasks, calculations, comparisons, sensing, or measurement values, etc., to enable or implement the technical operations or actions described herein. Operational or functional outcomes can be based on one or more inputs, stored data values, sensed or measured values, true or false indications, etc. While “program code” is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a specific task or implementing a specific abstract data type. In another non-limiting example, the controller may also include data storage components accessible by the processor, including memory, whether transient, volatile, or non-transient or non-volatile.

[0034] Additional non-limiting examples of memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc., or any suitable combination of these types of memory. In one example, program code may be stored in memory in a machine-readable format accessible to a processor. Furthermore, memory may store various types of data, sensed or measured data values, input, generated or processed data, etc., accessible to a processor when providing instructions, control, or operations to achieve a function or operable result, as described herein. In another non-limiting example, a controller may be configured to compare a first value with a second value and operate and control the operation of additional components based on the satisfaction of that comparison. For example, when a sensed, measured, or provided value is compared with another value (including a stored or predetermined value), the satisfaction of that comparison may result in an action, function, or operation that can be controlled by the controller.

[0035] Figure 1This is a schematic diagram of a gas turbine engine 10. As a non-limiting example, the gas turbine engine 10 can be used within an aircraft. The gas turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16 arranged in a series flow configuration. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the rotation axis 20 of the gas turbine engine 10.

[0036] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 can operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft and an HP drive shaft. The LP drive shaft can connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft can connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 can apply a driving force to the LP drive shaft, which in turn can rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 can apply a driving force to the HP drive shaft, which in turn can rotate the HP compressor 24.

[0037] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a shroud or housing that may extend circumferentially around and shield one or more sections of gas turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be possible. Furthermore, it is conceivable that any number of other components may be present within compressor section 12.

[0038] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of turbine section 16 may be circumferentially mounted to a shroud or housing. It should be noted that any number of blades, blades, and turbine stages are possible, as the illustrated turbine section 16 is merely schematic. Furthermore, it is conceivable that any number of other components may be present within turbine section 16.

[0039] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end. Combustion section 14 may include burner 30.

[0040] During operation of the gas turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 26 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the gas turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the gas turbine engine 10.

[0041] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a combustor 30, which has a surrounding structure around the gas turbine engine 10. Figure 1The combustor portions 31 are arranged in an annular configuration about the centerline or axis of rotation 20 of the gas turbine engine 10 (e.g., circumferentially spaced apart from each other in an annular configuration). In some configurations, the combustor portions 31 may include or be configured as a combustor cup, fuel cup, or nozzle cup. The combustor portions 31 may be arranged in an annular configuration about the axis of rotation 20. Fuel nozzle assemblies 48 may be connected to each combustor portion 31. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the combustor 30 may have a configuration similar to that of the gas turbine engine 10. Figure 1 The protective cover or housing 29 is positioned together with the protective cover or housing 29. The protective cover or housing 29 can shield or cover at least a portion of the combustion zone 14.

[0042] The burner 30 may be at least partially defined by a burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 and an inner bushing 42 arranged concentrically with respect to each other and in a ring-like manner around the engine centerline or axis of rotation 20. In some examples, the burner bushing 40 may have a ring-like structure that at least partially defines the burner 30. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 that is radially spaced from the inner bushing 42. In some examples, the burner bushing 40 may include a single bushing. The burner portion 31 may be arranged radially away from the axis of rotation 20, the radial distance being greater than the radial distance of the inner bushing 42 and less than the radial distance of the outer bushing 41. The combustion section centerline 33 of the combustion section 14 may be collinear with the axis of rotation 20. The centerline 33 of the combustion zone can define the radial direction R, the axial direction A, and the circumferential direction C.

[0043] The burner bushing 40 may at least partially define a combustion chamber 50 arranged annularly about the axis of rotation 20. For example, a wall 46 (e.g., a dome wall) may be substantially perpendicular to the axis of rotation 20 and may extend to an outer liner 41, an inner liner 42, or both to at least partially define the combustion chamber 50. The compressed air passage 32 may be at least partially defined by both the burner bushing 40 and the housing 29.

[0044] The burner 30 may include or be fluidly coupled to a first fuel supply section 34 (e.g., a first fuel manifold or conduit) supplying a first fuel F1, a second fuel supply section 36 (e.g., a second fuel manifold or circuit) supplying a second fuel F2, or both. For example, a fuel nozzle assembly 48 may include, or be fluidly coupled to, the first fuel supply section 34 and the second fuel supply section 36. The fuel nozzle assembly 48 fluidly connects the first fuel supply section 34 and the second fuel supply section 36 to one of the burner section 31 and the combustion chamber 50 to supply the combustion chamber 50 with the first fuel F1, the second fuel F2, or both. The fuel nozzle assembly 48 may be coupled to a wall 46. The first fuel F1 and the second fuel F2 may include any suitable fuel, including liquid fuels (such as Jet-A) or gaseous fuels (such as hydrogen fuel). In a non-limiting example, the hydrogen fuel may include 100% H2 (e.g., without diluent). In some examples, the first fuel F1 may include a liquid fuel (e.g., an atomized liquid fuel such as Jet-A) or a gaseous fuel (such as methane, which may be provided in the form of natural gas), and the second fuel F2 may include a gaseous fuel such as hydrogen. For example, the fuel nozzle assembly 48 may be a multi-fuel nozzle assembly, a liquid and gaseous fuel nozzle assembly, or a liquid and gaseous hydrogen fuel nozzle assembly. Additionally or alternatively, the first fuel supply unit 34 may be a liquid fuel supply unit, and the second fuel supply unit 36 ​​may be a gaseous hydrogen fuel supply unit. The controller 60 may be connected to the first fuel supply unit 34, the second fuel supply unit 36, the fuel nozzle assembly 48, or a combination thereof, and at least partially controls their operation. The controller 60 may include a processor 62 and a memory 64.

[0045] Figure 3 This is a schematic cross-sectional view of an example of one of the burner portions 31, which may be at least partially provided by the fuel nozzle assembly 48. The fuel nozzle assembly 48 may be directly or indirectly coupled to the wall 46 and the burner bushing 40. The fuel nozzle assembly 48 may include a fuel nozzle assembly centerline 35, which may be aligned with the combustion zone centerline 33. Figure 2 Parallel and radially offset. The centerline 35 of the fuel nozzle assembly may be collinear with the centerline of the burner portion 31 to which the fuel nozzle assembly 48 is connected or is part of it. The centerline 35 of the fuel nozzle assembly may define a second radial direction R2, a second axial direction A2, and a second circumferential direction C2. The second axial direction A2 may be parallel to the axial direction A( Figure 2 ).

[0046] The fuel nozzle assembly 48 includes a fuel nozzle 100 that supplies fuel (such as at least one of a first fuel F1 or a second fuel F2) and air 70 to the combustion chamber 50, and a main mixer 102 (e.g., a fuel-air mixer). The fuel nozzle 100 is configured such that the main mixer 102 is at least partially disposed around the fuel nozzle 100. For example, the fuel nozzle 100 includes an outer wall 110, and the main mixer 102 is coupled to an outer surface 112 of the outer wall 110 such that the main mixer 102 at least partially surrounds the fuel nozzle 100. The main mixer 102 is coupled to a wall 46, which allows the fuel nozzle assembly 48 to be coupled to the wall 46 and the burner bushing 40.

[0047] The main mixer 102 may be coupled to the wall 46 such that a cavity 120 (e.g., an annular cavity) is formed between the wall 46 and the main mixer 102. The wall 46 may include a first radial portion 130 coupled to the burner bushing 40 and extending radially inward in a second radial direction R2, a curved portion 132 extending radially inward and forward from the first radial portion 130, an axial portion 134 extending forward from the curved portion 132, and a second radial portion 136 extending radially inward from the front end of the axial portion 134. The main mixer 102 includes a main mixer wall 140, at least a portion of which extends in a second axial direction A2 and is disposed radially inside the axial portion 134. For example, the outer wall 110 and the main mixer wall 140 may at least partially define a main mixing chamber 142, which may have an annular configuration surrounding the fuel nozzle 100. The main mixer 102 may include a main swirler 144 (e.g., a main mixer swirler) coupled to the main mixer wall 140 to discharge swirling air 70 into the main mixing chamber 142. For example, the main swirler 144 may include a radial swirler configured to receive radially inwardly moving air 70 and discharge swirling air 70 radially inward, such as toward the outer surface 112 of the outer wall 110. The main mixing chamber 142 may receive swirling air 70 from the main swirler 144 and fuel (such as one or both of a first fuel F1 or a second fuel F2) from the fuel nozzle 100, and the air 70 and fuel may be mixed in the main mixing chamber 142 to form a main fuel-air mixture FA discharged from the outlet 146 of the main mixer 102 into the combustion chamber 50. The outlet 146 may be defined at the trailing edge 147 of the main mixer wall 140 between the main mixer wall 140 and the outer wall 110.

[0048] The main mixer wall 140, axial portion 134, and second radial portion 136 at least partially define the cavity 120. The wall 46 may include one or more flame-forming orifices, such as a first flame-forming orifice 148 and a second flame-forming orifice 149. The first flame-forming orifice 148 may be disposed in the second radial portion 136 to discharge air 70 into the cavity 120, such as rearward in the second axial direction A2. The second flame-forming orifice 149 may be disposed in the curved portion 132 to discharge air 70 into the combustion chamber 50 in a rearward and radially inward direction relative to the fuel nozzle assembly centerline 35. The first flame-forming orifice 148 may be in front of the second flame-forming orifice 149, the outlet 146 of the main mixer 102, or both. Additionally or alternatively, the first flame-forming orifice 148 may be radially inward of the second flame-forming orifice 149, radially outward of the outlet 146, rearward of the outer wall fuel orifice 158 of the outer wall 110, or a combination thereof. The second flame-forming orifice 149 may be located behind the outlet 146, the outer wall fuel orifice 158, or both. The first flame-forming orifice 148 and the second flame-forming orifice 149 may discharge air 70, which may promote flame forming in the combustion chamber 50. For example, air 70 from one or both of the first flame-forming orifice 148 and the second flame-forming orifice 149 may promote flame movement behind the wall 46 and radially inward of the burner bushing 40, which may limit the temperature at the wall 46 and the burner bushing 40, and limit flashback and flame retention. In some examples, the wall 46 may include a double-wall configuration, such as at the bend 132, and the second flame-forming orifice 149 may extend entirely through the double-wall configuration. The double-wall configuration may include a bend 132 and a second bend 138, the second bend 138 being spaced apart from the bend 132 and extending between the first radial portion 130 and the second radial portion 136. A wall cavity 139 may be defined between the bend 132 and the second bend 138. The first flame-forming hole 148 and the second flame-forming hole 149 may be a single hole (e.g., an annular hole), or may include multiple holes, such as multiple circumferentially spaced holes, or multiple rows or columns of circumferentially spaced holes.

[0049] refer to Figure 4-6 The outer wall 110 of the fuel nozzle 100 of the fuel nozzle assembly 48 may include a trailing edge 150 and may be shaped to define a pilot cone 152. For example, the pilot cone 152 may include an outer portion 154 and an inner portion 156 of the outer wall 110, the outer portion 154 and the inner portion 156 being configured in a forward-opening V-shape. The outer portion 154 may provide an outer surface 112 and include an outer wall fuel orifice 158. Figure 4-6 In the example shown, the outer wall fuel orifice 158 is shown as being fluidly connected to the second fuel supply unit 36, but the outer wall fuel orifice 58 may additionally or alternatively be connected to the first fuel supply unit 34. Figure 4 and Figure 6 Fluid connection. The outer wall fuel orifice 158 can be radially oriented to discharge fuel (such as at least one of first fuel F1 or second fuel F2) radially outward toward the main mixer wall 140 and into the main mixing chamber 142. The outer wall fuel orifice 158 can be directly radially oriented (e.g., to discharge fuel directly in the second radial direction R2), or it can be partially radially oriented (e.g., at an angle relative to the second radial direction R2 to discharge fuel radially outward and backward). The outer wall fuel orifice 158 can include a single orifice (e.g., an annular orifice) or multiple orifices, such as multiple circumferentially spaced orifices. The inner portion 156 can provide a tapered surface 160 that diverges toward the combustion chamber 50 to meet the outer portion 154. Fluidly connecting the fuel orifice (such as the outer wall fuel orifice 158) to both the first and second fuel supply sections 34, 36 allows the fuel nozzle assembly 48 to operate in multiple modes to discharge the first fuel F1 or the second fuel F2 from different locations during different operating conditions (e.g., flight conditions). Radially outward fuel discharge can promote a more uniform distribution of fuel in the combustion chamber 50, which can limit NO. x emission.

[0050] The outer wall 110 (e.g., the inner portion 156) may at least partially define the guide channel 170. The fuel nozzle 100 may include a secondary mixer 180, at least partially disposed in the guide channel 170, in fluid communication with the combustion chamber 50 (e.g., directly). The secondary mixer 180 may include a guide body 182 and a guide splitter 184. The guide body 182 may be aligned with the centerline 35 of the fuel nozzle assembly. The guide splitter 184 may be at least partially radially disposed between the guide body 182 and the outer wall 110 to divide the guide channel 170 into a first guide channel segment 172 between the guide body 182 and the guide splitter 184, and a second guide channel segment 174 between the guide splitter 184 and the inner portion 156 of the outer wall 110.

[0051] The guide body 182 may include an ignition fuel orifice 186, which may be fluidly connected to the first fuel supply section 34 and the second fuel supply section 36. The ignition fuel orifice 186 may be axially oriented to discharge fuel in a second axial direction A2. Figure 4 and Figure 6 ), or it can have an orientation with a radial component ( Figure 5 This causes the ignition fuel orifice 186 to discharge fuel (such as at least one of first fuel F1 or second fuel F2) in a direction offset from the second axial direction A2 and the second radial direction R2, and into the guide channel 170. This is achieved through a radially oriented configuration ( Figure 5The ignition orifice 186 can discharge fuel toward the guide splitter 184, such as by cross-flowing with air 70 flowing through the first guide channel section 172. This cross-flow can promote mixing of fuel and air 70, which can limit temperature and NO. x Discharge. The ignition fuel orifice 186 may include a single fuel orifice (e.g., an axially oriented central orifice or a radially oriented annular orifice) or multiple orifices, which may include one or more axially oriented orifices, one or more radially oriented orifices, or a combination thereof. The ignition fuel orifice 186 may be fluidly coupled to the first fuel supply section 34, the second fuel supply section 36, or both. The guide splitter 184 may include a convergent-divergent configuration and may extend axially rearward of the guide body 182. The trailing edge 150 may be located behind the rear end of the guide splitter 184.

[0052] Fluidly connecting the fuel orifice (such as the outer wall fuel orifice 158, the ignition fuel orifice 186, or a combination thereof) to both the first and second fuel supply sections 34, 36 allows the fuel nozzle assembly 48 to operate in multiple modes to discharge the first fuel F1 or the second fuel F2 from different locations during different operating conditions (e.g., flight conditions). Radially outward fuel discharge can promote a more uniform distribution of fuel in the combustion chamber 50, which can limit NO. x emission.

[0053] The secondary mixer 180 may include a first guide swirler 200, a second guide swirler 202, or both. The first guide swirler 200 may be disposed at least partially between the guide body 182 and the guide splitter 184 in the guide channel 170. The second guide swirler 202 may be disposed at least partially between the guide splitter 184 and the outer wall 110 (e.g., the inner portion 156) in the guide channel 170. The first and second guide swirlers 200, 202 may be axial swirlers that receive air 70 moving in a second axial direction A2 and output swirling air 70 in the second axial direction A2 into the guide channel 170. The guide splitter 184 may include a splitter fuel orifice 210 (… Figure 4 and Figure 6 The splitter fuel orifice 210 can be located at the trailing edge 188 of the guide splitter 184 and can be oriented to have a radial component (e.g., radial orientation). For example, the trailing edge of the guide splitter 184 can be at least radially outward at an angle, such that the first or second fuel F1, F2 discharged from the splitter fuel orifice 210 is guided radially outward and axially rearward. The splitter fuel orifice 210 ( Figure 4 and Figure 6It can be fluidly connected to the first fuel supply unit 34, the second fuel supply unit 36, or both, to discharge the first fuel F1, the second fuel F2, or both into the guide channel 170, toward the combustion chamber 50, to discharge the first fuel F1, the second fuel F2, or both, or both. Diverter fuel orifice 210 ( Figure 4 and Figure 6 It may include an annular orifice or multiple circumferentially spaced orifices.

[0054] refer to Figure 4 and Figure 5 The outer wall 110 may define a recess 220 (e.g., a radial recess). For example, the outer wall 110 may include a first angled surface 222 and a second angled surface 224 configured with a radially outwardly opening V-shape. The first angled surface 222 may be angled such that the first angled surface 222 faces radially outward and rearward. The second angled surface 224 may be angled such that the second angled surface 224 faces radially outward and forward. An outer wall fuel orifice 158 may be provided at the first angled surface 222 such that the outer wall fuel orifice 156 is partially radially oriented to discharge first fuel F1, second fuel F2, or both radially outward and rearward (e.g., to discharge fuel radially outward and forward). In some examples, the outer wall fuel orifice 158 may be provided on the second angled surface 224, or on both the first and second angled surfaces 222 and 224.

[0055] refer to Figure 5 The outer wall 110 may include a trailing edge fuel orifice 230 located at a trailing edge 150. The trailing edge fuel orifice 230 may be axially oriented or at least partially radially oriented, discharging fuel (such as a second fuel F2) into the combustion chamber 50. The trailing edge fuel orifice 230 is located behind the outer wall fuel orifice 158, which is behind the ignition fuel orifice 186, providing an axially staged fuel injection configuration. This axially staged configuration can provide different mixing lengths and times for the fuel and air 70, which can provide better flame stability (e.g., via shorter mixing lengths and times) and lower temperatures and NO. x Emissions (e.g., via longer mixing lengths and times).

[0056] refer to Figure 6 The outer wall fuel orifice 158 may be aligned with a second radial direction (R2) (e.g., direct radial orientation) and fluidly connected to the second fuel supply section 36 to discharge the second fuel F2 into the main mixing chamber 142. In some examples, the outer wall fuel orifice 158 may additionally or alternatively be fluidly connected to the first fuel supply section 34 to discharge the first fuel F1 into the main mixing chamber 142.

[0057] refer to Figure 7 The outer wall fuel orifice 158 of the outer wall 110 of the fuel nozzle 100 can be directly radially oriented (e.g., parallel to the second radial direction R2) and can be fluidly connected to the second fuel supply section 36 to discharge the second fuel F2 directly radially outward toward the main mixer wall 140 of the main mixer 102 and into the main mixing chamber 142 to mix with air 70 and form a fuel-air mixture FA. The ignition fuel orifice 186, the distributor fuel orifice 210, or both of the guide body 182 can be fluidly connected to the first fuel supply section 34 to discharge the first fuel F1 into the guide channel 170, the combustion chamber 50, or both. For example, the first fuel F1 may include natural gas.

[0058] refer to Figure 8 and Figure 9 The outer wall 110 of the fuel nozzle 100 may include a set of second fuel orifices 240. These second fuel orifices 240 may discharge fuel (such as at least one of first fuel F1 or second fuel F2) into the guide channel 170, the combustion chamber 50, or both. Figure 8 and Figure 9 In the example shown, the set of second fuel orifices 240 is shown as being fluidly connected to the second fuel supply unit 36, but the set of second fuel orifices 240 may additionally or alternatively be connected to the first fuel supply unit 34. Figure 8 Fluid connection. The set of second fuel orifices 240 may be disposed at the conical surface 160 of the guide cone 152. The set of second fuel orifices 240 may include orifices that are axially spaced, radially spaced, circumferentially spaced, or a combination thereof. The set of second fuel orifices 240 may be axially oriented to discharge fuel in a second axial direction A2, or at least partially radially oriented to discharge fuel radially inward toward at least a certain extent toward the fuel nozzle assembly centerline 35. In some examples, the set of second fuel orifices 240 may be angled to create crossflow with air 70 flowing radially outward and backward in the guide channel 170 (such as swirling air 70 from the second guide swirler 202 flowing along the conical surface 160). The outer wall fuel orifice 158 and the set of second fuel orifices 240 may be fluidly connected to the second fuel supply section 36 to discharge the second fuel F2 into the main mixing chamber 142 and the guide channel 170, respectively. Reference Figure 8 The ignition fuel orifice 186 of the guide body 182 can be fluidly connected to the first fuel supply section 34 to discharge the first fuel F1 (e.g., liquid fuel or natural gas) into the guide channel 170, the combustion chamber 50, or both. (See reference) Figure 9The ignition fuel orifice 186 of the guide body 182 can be fluidly connected to the second fuel supply section 36 to discharge the second fuel F2 (e.g., gaseous hydrogen) into the guide channel 170. For example, the fuel nozzle assembly 48 can discharge the second fuel F2 through all fuel orifices 158, 186, 240, such as without discharging the first fuel F1 ( Figure 8 ).

[0059] refer to Figure 10 This illustrates a method 1000 for operating a gas turbine engine. Method 1000 can be used with, for example,... Figure 1-9 The gas turbine engine 10 and its components are generally shown in the diagram. Method 1000 may include, for example, supplying a first fuel F1 from a first fuel supply unit 34 to a fuel nozzle assembly 48 (box 1002). Additionally or alternatively, method 1000 may include supplying a second fuel F2, for example, from a second fuel supply unit 36 ​​to the fuel nozzle assembly 48 (box 1004).

[0060] Method 1000 may include discharging fuel (such as first fuel F1, second fuel F2, or both) from fuel nozzle 100 into combustion chamber 50 (box 1006), which may include discharging fuel into main mixing chamber 142, guide channel 170, or a combination thereof via one or more fuel orifices 158, 186, 210, 240. Discharging first fuel F1 (e.g., liquid fuel or natural gas) from fuel nozzle 100 may include discharging first fuel F1 from ignition fuel orifice 186 toward combustion chamber 50 into guide channel 170 in a second axial direction A2 of fuel nozzle assembly 48. Additionally or alternatively, discharging first fuel F1 from fuel nozzle 100 may include discharging first fuel F1 radially outward and rearward from splitter fuel orifice 210. Fuel discharged from the ignition fuel orifice 186, the distributor fuel orifice 210, or both may be mixed with air 70 (such as swirling air 70 from one or both of the first guide swirler 200 or the second guide swirler 202) in the guide channel 170 before entering the combustion chamber 50, may be mixed with air 70 in the combustion chamber 50, or both.

[0061] Discharging a second fuel F2 (e.g., hydrogen) into the combustion chamber 50 may include discharging the second fuel F2 radially outward from the outer surface 112 of the fuel nozzle 100 (such as from the outer wall fuel orifice 158 toward the main mixer wall 140). Radially outward discharging of the second fuel F2 may include direct radial outward discharging or radial outward and rearward discharging of the second fuel F2. Additionally or alternatively, discharging the second fuel F2 into the combustion chamber 50 may include discharging the second fuel F2 from one or more of the ignition fuel orifice 186, the distributor fuel orifice 210, or the group of second fuel orifices 240. In some examples, the fuel nozzle 100 may discharge the first fuel F1 and the second fuel F2 through the ignition fuel orifice 186. For example, the fuel nozzle 100 may discharge the first fuel F1 through an axially oriented orifice of the ignition fuel orifice 186, and the fuel nozzle 100 may discharge the second fuel F2 through one or more radially oriented orifices of the ignition fuel orifice 186.

[0062] Method 1000 may include identifying changes in operating parameters of the gas turbine engine 10 or a vehicle (e.g., an aircraft) coupled thereto (box 1008). This change may be identified via controller 60, one or more sensors communicating with controller 60, or a combination thereof. Operating parameters may include thrust demand, the amount of available first fuel F1, the amount of available second fuel F2, or one or more other parameters. In response to identifying changes in operating parameters, method 1000 may include adjusting fuel output (box 1010), which may include supplying different amounts of first fuel F1 and second fuel F2, or a combination thereof, to one or more fuel orifices 158, 186, 210, 240 using different amounts of first fuel F1 and second fuel F2, or a combination thereof (box 1010). For example, if the controller 60 determines that the amount of first fuel F1 discharged through the ignition fuel orifice 186 and the distributor fuel orifice 210 is insufficient, the controller 60 may control one or more of the first fuel supply unit 34, the second fuel supply unit 36, or the fuel nozzle 100 to supply first fuel F1 only to the ignition fuel orifice 186, or to supply second fuel F2 to one or both of the ignition fuel orifice 186 and the distributor fuel orifice 210.

[0063] In some examples, controller 60 can adjust fuel output by controlling the fuel nozzle assembly 48 to release a second fuel F2 (e.g., hydrogen) during certain phases of flight (such as approach), which can limit coking by removing unburned liquid fuel from the combustion zone. Utilizing hydrogen fuel alone during certain phases of flight (such as cruise and approach) can achieve zero carbon emissions (e.g., zero CO2). Utilizing hydrogen fuel can shorten the length of burner 30 because mixing time can be reduced. Utilizing hydrogen fuel alone at low power can limit or prevent smog. Utilizing liquid fuel (e.g., first fuel F1) during at least some phases of flight (such as takeoff and climb) can limit temperature to improve durability and limit NO. x emission.

[0064] Although a turbine engine has been described, it should be understood that the combustor described herein can be used in any engine having a combustor. It should also be understood that the application of the disclosed aspects discussed herein also applies to engines having a propeller section or a fan and supercharger section, as well as turbojet engines and turbocharged engines.

[0065] Within the scope not described herein, different features and structures of various embodiments may be combined or substituted for each other as needed. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown so, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure.

[0066] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and methods of making any combinations. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0067] Further details are provided by the following topics:

[0068] A gas turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a tandem flow configuration, wherein the combustion section includes: a combustor bushing that at least partially defines a combustion chamber; a wall coupled to the combustor bushing; a first fuel supply section that supplies a first fuel; a gaseous fuel supply section that supplies gaseous hydrogen fuel; and a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply section and the gaseous fuel supply section, the fuel nozzle assembly including: a main mixer; and a fuel nozzle configured such that the main mixer is at least partially disposed around the fuel nozzle, the fuel nozzle including: an outer wall that defines a guide channel; an outer wall fuel orifice extending through the outer wall and fluidly coupled to the first fuel supply section and the gaseous fuel supply section to radially outwardly discharge at least one of the first fuel or the gaseous hydrogen fuel into the main mixer; and a secondary mixer disposed in the guide channel.

[0069] The gas turbine engine according to any of the foregoing clauses, wherein the first fuel comprises natural gas or liquid fuel.

[0070] In any of the preceding clauses of the gas turbine engine, the main mixer is coupled to the wall such that a cavity is provided between the main mixer and the wall.

[0071] According to any of the preceding clauses, the trailing edge of the outer wall includes a trailing edge fuel orifice behind the outer wall fuel orifice.

[0072] In any of the foregoing clauses, the gas turbine engine wherein the trailing edge fuel orifice points radially outward.

[0073] In any of the preceding clauses of the gas turbine engine, the trailing edge of the outer wall is located behind the outlet of the main mixer.

[0074] According to any of the preceding clauses, the gas turbine engine includes a guide body and guide splitters spaced radially outward from the guide body; and the guide body includes an ignition fuel orifice fluidly connected to at least one of the first fuel supply or the gas fuel supply.

[0075] According to any of the preceding clauses, in a gas turbine engine, the ignition fuel orifice is directly radially outward toward the guide splitter to discharge the first fuel or the gaseous hydrogen fuel in a manner that cross-flows with the air flowing through the guide channel.

[0076] According to any of the preceding clauses, the gas turbine engine, wherein the secondary mixer includes a first guide vortex disposed between the guide splitter and the guide body, and a second guide vortex disposed between the guide splitter and the outer wall.

[0077] The gas turbine engine according to any of the foregoing clauses, wherein the main mixer includes a main mixer swirler; and wherein the main mixer swirler is a radial swirler, and the first guide swirler and the second guide swirler are axial swirlers.

[0078] In any of the preceding clauses of the gas turbine engine, the guide splitter includes a splitter fuel orifice that is fluidly connected to at least one of the first fuel supply unit or the gas fuel supply unit.

[0079] The gas turbine engine according to any of the foregoing clauses, wherein the outer wall at least partially defines a guide cone including a set of second fuel orifices.

[0080] In any of the foregoing clauses, the gas turbine engine wherein the set of second fuel orifices is fluidly connected to the gas fuel supply unit.

[0081] According to any of the preceding clauses, in a gas turbine engine, the set of second fuel orifices is configured to discharge the gaseous hydrogen fuel in a manner that cross-flows with air discharged from a guide cyclone, the guide cyclone being disposed in the guide channel in front of the set of second fuel orifices.

[0082] A gas turbine engine according to any of the foregoing clauses, wherein the wall includes a first flame-forming hole behind the fuel orifice of the outer wall.

[0083] According to any of the preceding clauses, the gas turbine engine, wherein the wall includes a second flame-forming hole, the second flame-forming hole being located behind the first flame-forming hole and pointing radially inward.

[0084] In any of the preceding clauses of the gas turbine engine, the second flame-forming orifice is located behind the outlet of the main mixer.

[0085] According to any of the preceding clauses, the gas turbine engine wherein the first flame-forming orifice is radially outside and in front of the outlet of the main mixer; and wherein the second flame-forming orifice is radially outside the first flame-forming orifice.

[0086] A gas turbine engine according to any of the foregoing clauses, wherein the main mixer and the wall define a cavity; and wherein the first flame-forming orifice extends through the wall to discharge air into the cavity.

[0087] In a gas turbine engine according to any of the foregoing clauses, the outer wall defines a radial recess, and the outer wall fuel orifice is disposed in the radial recess.

[0088] The gas turbine engine according to any of the foregoing clauses, wherein the wall includes a first radial portion, a first curved portion, an axial portion, and a second curved portion.

[0089] The gas turbine engine according to any of the foregoing clauses, wherein the first curved portion and the second curved portion are configured with a double-wall structure.

[0090] The gas turbine engine according to any of the foregoing clauses, wherein the outer wall includes a trailing edge defining a guide cone.

[0091] According to any of the preceding clauses of the gas turbine engine, wherein the fuel nozzle assembly includes a guide splitter that is at least partially radially disposed between the guide body and the outer wall to divide the guide channel into a first guide channel segment between the guide body and the guide splitter, and a second guide channel segment between the guide splitter and the inner portion of the outer wall.

[0092] According to any of the preceding clauses, in a gas turbine engine, the outer wall defines a recess, the recess including a first angled surface and a second angled surface configured in a radially outwardly opening V-shape.

[0093] According to any of the preceding clauses, the gas turbine engine wherein the first angled surface is angled such that the first angled surface faces radially outward and rearward; and wherein the second angled surface is angled such that the second angled surface faces radially outward and forward.

[0094] According to any of the preceding clauses, in a gas turbine engine, the outer wall fuel orifice is disposed at the first angled surface such that the outer wall fuel orifice is partially radially oriented to discharge the first fuel, the second fuel, or both radially outward and rearward.

[0095] According to any of the preceding clauses, in a gas turbine engine, the outer wall fuel orifice is disposed at the second angled surface such that the outer wall fuel orifice is partially radially oriented to discharge the first fuel, the second fuel, or both radially outward and forward.

[0096] A fuel nozzle assembly for a gas turbine engine, the fuel nozzle assembly comprising: a primary mixer; and a fuel nozzle configured such that the primary mixer is at least partially disposed around the fuel nozzle, the fuel nozzle comprising: an outer wall defining a guide channel; an outer wall fuel orifice extending through the outer wall to radially outwardly discharge at least one of a first fuel or gaseous hydrogen fuel into the primary mixer; and a secondary mixer disposed in the guide channel.

[0097] The fuel nozzle assembly according to any of the foregoing clauses, wherein the first fuel comprises natural gas or liquid fuel.

[0098] According to any of the preceding clauses, the fuel nozzle assembly wherein the main mixer is configured to be coupled to a wall such that a cavity is provided between the main mixer and the wall.

[0099] According to any of the preceding clauses, the trailing edge of the outer wall includes a trailing edge fuel orifice behind the outer wall fuel orifice.

[0100] According to any of the foregoing clauses, the trailing edge fuel orifice is radially outward.

[0101] According to any of the foregoing clauses, the trailing edge of the outer wall is located behind the outlet of the main mixer.

[0102] According to any of the preceding clauses, the fuel nozzle assembly includes a guide body and guide splitters spaced radially outward from the guide body; and the guide body includes an ignition fuel orifice fluidly connected to at least one of the first fuel supply or the gaseous fuel supply.

[0103] According to any of the preceding clauses, the fuel nozzle assembly wherein the ignition fuel orifice is directly radially outward toward the guide splitter to discharge the first fuel or the gaseous hydrogen fuel in a manner that cross-flows with the air flowing through the guide channel.

[0104] According to any of the preceding clauses, the fuel nozzle assembly, wherein the secondary mixer includes a first guide vortex disposed between the guide splitter and the guide body, and a second guide vortex disposed between the guide splitter and the outer wall.

[0105] The fuel nozzle assembly according to any of the foregoing clauses, wherein the main mixer includes a main mixer swirler; and wherein the main mixer swirler is a radial swirler, and the first guide swirler and the second guide swirler are axial swirlers.

[0106] According to any of the preceding clauses, the fuel nozzle assembly wherein the guide splitter includes a splitter fuel orifice fluidly connected to at least one of the first fuel supply unit or the gas fuel supply unit.

[0107] According to any of the preceding clauses, the fuel nozzle assembly wherein the outer wall at least partially defines a guide cone comprising a set of second fuel orifices.

[0108] The fuel nozzle assembly according to any of the foregoing clauses, wherein the set of second fuel orifices is fluidly connected to the gas fuel supply section.

[0109] According to any of the preceding clauses, the set of second fuel orifices is configured to discharge the gaseous hydrogen fuel in a manner that cross-flows with air discharged from a guide cyclone, the guide cyclone being disposed in the guide channel in front of the set of second fuel orifices.

[0110] According to any of the foregoing clauses, the fuel nozzle assembly, wherein the wall includes a first flame-forming hole behind the outer wall fuel orifice.

[0111] According to any of the preceding clauses, the fuel nozzle assembly wherein the wall includes a second flame-forming orifice, the second flame-forming orifice being located behind the first flame-forming orifice and pointing radially inward.

[0112] According to any of the foregoing clauses, the fuel nozzle assembly wherein the second flame-forming orifice is located behind the outlet of the main mixer.

[0113] According to any of the preceding clauses, the fuel nozzle assembly wherein the first flame-forming orifice is radially outside and in front of the outlet of the main mixer; and wherein the second flame-forming orifice is radially outside the first flame-forming orifice.

[0114] The fuel nozzle assembly according to any of the foregoing clauses, wherein the main mixer and the wall define a cavity; and wherein the first flame-forming orifice extends through the wall to discharge air into the cavity.

[0115] According to any of the preceding clauses, the fuel nozzle assembly wherein the outer wall defines a radial recess, and the outer wall fuel orifice is disposed in the radial recess.

[0116] A method of operating a gas turbine engine according to any of the preceding clauses, the method comprising supplying a first fuel to the fuel nozzle assembly; supplying a second fuel to the fuel nozzle assembly; discharging fuel into the combustion chamber; identifying changes in operating parameters; and utilizing different fuel orifices, different fuels, or both.

[0117] An electronic controller configured to implement the method according to any of the foregoing clauses.

[0118] An electronic controller configured to control the operation of a gas turbine engine according to any of the preceding clauses.

[0119] An electronic controller configured to control the operation of a fuel nozzle assembly according to any of the preceding clauses.

[0120] An electronic controller according to any of the foregoing clauses includes a processor and a memory.

Claims

1. A gas turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section includes: A burner bushing that at least partially defines a combustion chamber; The wall is connected to the burner bushing; First fuel supply unit, which supplies first fuel; A gaseous fuel supply unit, which supplies gaseous hydrogen fuel; and A fuel nozzle assembly, connected to the wall and fluidly connected to the first fuel supply unit and the gaseous fuel supply unit, the fuel nozzle assembly comprising: The main mixer; and A fuel nozzle, the fuel nozzle being configured such that the main mixer is at least partially disposed around the fuel nozzle, the fuel nozzle comprising: Outer wall, the outer wall defining a guide channel; An outer wall fuel orifice, extending through the outer wall and fluidly connected to the first fuel supply section and the gaseous fuel supply section, for radially outward discharge of at least one of the first fuel or the gaseous hydrogen fuel into the main mixer; and A secondary mixer is disposed in the guide channel.

2. The gas turbine engine according to claim 1, characterized in that, in, The first fuel includes natural gas or liquid fuel.

3. The gas turbine engine according to claim 1, characterized in that, in, The main mixer is connected to the wall, thereby providing a cavity between the main mixer and the wall.

4. The gas turbine engine according to claim 1, characterized in that, in, The trailing edge of the outer wall includes the trailing edge fuel orifice behind the outer wall fuel orifice.

5. The gas turbine engine according to claim 4, characterized in that, in, The trailing edge fuel orifice points radially outward.

6. The gas turbine engine according to claim 4, characterized in that, in, The trailing edge of the outer wall is located behind the outlet of the main mixer.

7. The gas turbine engine according to claim 1, characterized in that, in, The secondary mixer includes a guide body and guide splitters spaced radially outward from the guide body; and The guide body includes an ignition fuel orifice that is fluidly connected to at least one of the first fuel supply unit or the gas fuel supply unit.

8. The gas turbine engine according to claim 7, characterized in that, in, The ignition fuel orifice faces directly radially outward toward the guide splitter, discharging the first fuel or the gaseous hydrogen fuel in a manner that cross-flows with the air flowing through the guide channel.

9. The gas turbine engine according to claim 7, characterized in that, in, The secondary mixer includes a first guide vortex disposed between the guide splitter and the guide body, and a second guide vortex disposed between the guide splitter and the outer wall.

10. The gas turbine engine according to claim 9, characterized in that, in, The main mixer includes a main mixer cyclone separator; and The main mixer cyclone is a radial cyclone, and the first guide cyclone and the second guide cyclone are axial cyclones.

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